طراحی یک چندپره هیبرید سنگین‌وزن با برد و قابلیت حمل بار بالا جهت استفاده در مدیریت بحران

نوع مقاله : مقاله پژوهشی

نویسندگان

1 دانشجوی دکتری / دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران

2 عضو هیات علمی / دانشکده مهندسی هوافضا، دانشگاه صنعتی امیرکبیر، تهران، ایران

3 کارشناس ارشد / پژوهشکده سامانه‌های حمل‌ونقل فضایی، پژوهشگاه فضایی، تهران، ایران

چکیده

در این مقاله، طراحی مفهومی یک چندپره بدون سرنشین با ساختاری جدید که کاربرد اصلی آن مدیریت بحران است، انجام می‌شود. بُرد پروازی این چندپره 400 کیلومتر (200 کیلومتر رفت و 200 کیلومتر برگشت) بوده و قابلیت حمل 800 کیلوگرم بار را دارد. همچنین سرعت پرواز مستقیم آن 100 کیلومتر بر ساعت است. تاکنون چندپره‌ای با ویژگی‌های عملکردی ذکرشده طراحی نشده‌است. با توجه به عملکرد تعریف‌شده، سیستم پیشران الکتریکی قابل‌استفاده نبوده و سیستم پیشران هیبرید برای این چندپره مناسب است. با بررسی بیشتر در مورد انواع روش‌های هیبریدسازی، سیستم پیشران هیبرید بدون تبدیل انرژی به عنوان طرح پیشنهادی انتخاب شد. طراحی مفهومی مبتنی بر وزن برخاست انجام می‌شود یعنی ابتدا وزن برخاست تخمین زده شده و سپس براساس آن زیرسیستم‌های چندپره طراحی می‌شوند. در نهایت جمع کل وزن زیرسیستم‌ها با مقدار تخمینی وزن برخاست مقایسه می‌شود. در صورت تفاوت زیاد، روند دوباره تکرار می‌شود تا در نهایت دو عدد همگرا شوند. در این مقاله آخرین حلقه طراحی ارائه‌شده و مشخصات سیستم پیشران الکتریکی، سیستم پیشران سوختی، سیستم انتقال قدرت و سازه محاسبه می‌شود.

کلیدواژه‌ها

موضوعات

عنوان مقاله [English]

Design of a Hybrid Heavy Multirotor with Long Range and High Payload Carrying Capacity for Using in Disaster Management

نویسندگان [English]

  • Sepehr Saadat 1
  • Sayyed Majid Esmailifar 2
  • Fariborz Masroor 3
1 Department of Aerospace Engineering, Amirkabir University of Science and Technology, Tehran, Iran
2 Aerospace Engineering Department,, Amirkabir University of Technology, Tehran, Iran
3 Space Transportation Research Institute, Iranian Space Research Center, Tehran, Iran
چکیده [English]

This study presents the conceptual design of an unmanned multirotor with a novel configuration whose main application is disaster management. This multirotor can carry 800 kg of cargo for a range of 400 km, and its forward flight speed is 100 km/h. A multirotor with the specified performance parameters has not yet been developed. Due to the stipulated performance, the electric propulsion system is inapplicable, and a hybrid propulsion system is considered for this multirotor. The hybrid propulsion system without energy conversion was selected for the proposed design after further investigating alternative hybridization approaches. Multirotor subsystems are conceptually designed based on take-off weight, i.e., take-off weight is first estimated, and then multirotor subsystems are designed based on it. Finally, the overall subsystems’ weight is compared to the predicted take-off weight. If there is a significant discrepancy, the procedure is repeated until the two values converge. This paper presents the last design loop, and the specifications of the electric propulsion system, fuel propulsion system, power transmission system, body structure, and skid are calculated.

کلیدواژه‌ها [English]

  • Super Heavy Multirotor
  • Hybrid Propulsion System
  • Conceptual Design
  • Disaster Management

مراجع

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